Experimental Studies of Film Cooling in Supersonic Combustors

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Experimental Studies of Film Cooling in Supersonic Combustors
	Fan C(樊川); Wang J(王晶); Fan XJ(范学军)
	2017
会议日期	6-9 March 2017
会议地点	Xiamen, China
关键词	Combustion Combustors Coolants Kerosene Spacecraft Supersonic Aerodynamics
英文摘要	The current work is an experimental investigation of the dependence of film-cooling effectiveness on the injection angle, mass flux and injection temperature in supersonic combustors. The mainstream Mach number is 2.5, and the coolant was injected with sonic speed. The total temperature of the mainstream is 1500K, and for the injection it ranges from 300K to 1060K. Three injection angle is respectively 00, 430, 1370. The coolant mass flux ranges from 1% to 6% of the mainstream mass flux, and the mainstream mass flux is 2.5kg/s. The results show that a smaller injection angle has a better performance in film cooling effectiveness and indicate that an increase in film-cooling effectiveness with the increase of the coolant mass flux. The influence of coolant temperature is more complex. The rising of coolant temperature reduces the film-cooling effectiveness without kerosene combustion, while has not significant difference with kerosene combustion. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
会议录	21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
会议录出版者	American Institute of Aeronautics and Astronautics Inc, AIAA
会议录出版地	USA
语种	英语
URL标识	查看原文
ISBN号	978-1-62410-463-3
内容类型	会议论文
源URL	[http://dspace.imech.ac.cn/handle/311007/72186]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beisihuanxilu NO.15, Beijing 2.100190, China
推荐引用方式 GB/T 7714	Fan C,Wang J,Fan XJ. Experimental Studies of Film Cooling in Supersonic Combustors[C]. 见:. Xiamen, China. 6-9 March 2017.